|Publication number||US7597285 B2|
|Application number||US 10/543,037|
|Publication date||Oct 6, 2009|
|Filing date||Jan 21, 2004|
|Priority date||Jan 23, 2003|
|Also published as||CA2513764A1, CA2513764C, CN1845848A, CN1845848B, DE10302514A1, DE10302514B4, US20060049307, WO2004065209A1|
|Publication number||10543037, 543037, PCT/2004/93, PCT/DE/2004/000093, PCT/DE/2004/00093, PCT/DE/4/000093, PCT/DE/4/00093, PCT/DE2004/000093, PCT/DE2004/00093, PCT/DE2004000093, PCT/DE200400093, PCT/DE4/000093, PCT/DE4/00093, PCT/DE4000093, PCT/DE400093, US 7597285 B2, US 7597285B2, US-B2-7597285, US7597285 B2, US7597285B2|
|Original Assignee||Airbus Deutschland Gmbh|
|Export Citation||BiBTeX, EndNote, RefMan|
|Patent Citations (30), Referenced by (14), Classifications (24), Legal Events (5)|
|External Links: USPTO, USPTO Assignment, Espacenet|
The invention relates to a fluid dynamically effective surface of a device moving in a fluid, especially a flying machine, especially a supporting or lifting surface of a flying machine, whereby the surface comprises an elastic axis extending in the span direction of the surface and an adjustable control surface.
In connection with a device moving in a fluid, there arises during the movement through the fluid, thus perhaps in connection with a flying machine during flight, a deformation of the fluid dynamically effective surface, thus of the lifting surface of the flying machine. This deformation is variable or changeable and depends on the effective aerodynamic forces and the inertial and/or mass forces. These are dependent on the flight condition (speed, altitude), as well as on the loading condition (useful payload, fuel quantity, position of center of gravity). Without special measures, a wing can only be designed so that it comprises the deformation that is most advantageous for the aerodynamic resistance or drag only for a single condition and time point of a flight. A different deformation, which is not drag-minimal, arises for every other condition and for every other time point.
In the state of the art, no systems have previously become known, with which the structural deformation of wings can be adapted or matched to a form or shape that is optimal for the aerodynamic resistance or drag. The influence of the structural deformation was either neglected or disregarded, simply put up with, or in the best case taken into consideration such that the deformation that is most advantageous for the aerodynamic drag arises for an “average” flight condition (average loading, half flight time).
While, of course, control surfaces that are per se adjustable are known on such fluid dynamically effective surfaces such as the lifting surface of a flying machine, these, however, serve for the control of the flight attitude or the trimming of the aircraft, but not, however, a change or variation of the deformation of the wing in the sense of an adaptation or matching to the form that is most advantageous for the aerodynamic drag dependent on the flight and loading condition. It is also known, to use conventional control surfaces on the wing trailing edge (aileron) for influencing the aerodynamic pressure distribution for a smaller structural loading (load reduction), a similar control surface concept has also become known for improving the roll control for an experimental version of a combat aircraft, similarly also for the same purpose the additional use of flaps along the wing leading edge.
The aerodynamic pressure distribution and the structural loading change or vary due to differing flight conditions (altitude, speed) and loading conditions (useful payload, fuel, position of center of gravity), whereby different elastic deformations arise. This deformation condition influences the aerodynamic (lift induced) resistance. For a given span, and without consideration of the structural loading, the minimal resistance arises for an elliptical aerodynamic pressure distribution over the span. This can be achieved through an elliptical wing plan form or through a corresponding torsion or twisting of the wing profile chord in the span direction relative to the direction of incident flow or relative wind. A wing torsion deformation in the span direction (twisting) as well as a bending deformation on the swept-back wing influence this distribution. Therefore, the drag-minimizing deformation condition can only prevail for a short time during the total duration of a flight, in which the fuel quantity changes and the flying proceeds with different speeds at different altitudes. Moreover, the magnitude of the deformation is dependent on the loading condition.
The object of the invention is to present a fluid dynamically effective surface of a device moving in a fluid, especially a flying machine, especially a lifting surface of a flying machine, which comprises a deformation that is most advantageous for a minimal fluid dynamic drag, to the extent possible for every condition.
The above object has been achieved through the invention whereby there is provided a fluid dynamically effective surface of a device moving in a fluid, especially a flying machine, especially a lifting surface of a flying machine. The surface comprises an elastic axis extending in the span direction of the surface, and an adjustable control surface. According to the invention it is provided that the surface is elastically deformable in the bending direction and/or in the direction about the elastic axis, dependent on the adjustment of the control surface, in connection with change of the induced fluid dynamic drag and that a control and/or regulating device for adjusting the control surface in the sense of a minimization of the induced fluid dynamic drag of the surface is provided. A significant advantage of the inventive fluid dynamic surface is that a distribution of the lift force over the wing span, which distribution is optimal for the drag or resistance, can be produced for practically every flight and loading condition. For the lifting surface of an aircraft this means that an adaptation of the deformation can be achieved for practically every flight condition through the invention. Moreover, the invention can be used to advantage for additional functions, such as the support or assistance of the roll control, a load reduction, an improvement of the flutter stability, and a use for the stabilization and/or control of the lateral movement about the aircraft vertical axis, in case the plane of the control surface comprises a vertical component.
Preferably, the control surface is arranged offset by a prescribed spacing distance relative to the elastic axis.
Preferably the control surface is arranged supported rotatably about a rotation axis, and the rotation axis or at least a component thereof extends in the direction of the elastic axis.
According to an embodiment of the invention, the control surface can be arranged by a prescribed spacing distance behind the elastic axis.
According to a preferred embodiment of the invention, the control surface is arranged by a prescribed spacing distance in front of the elastic axis. The mounting of the control surface in front of the elastic axis means that the wing deformation supports or assists the desired aerodynamic force effect, while the aerodynamic force from the deformation acts contrary to the desired direction in connection with a position of the control surface behind the elastic axis.
According to an embodiment of the invention, the control surface can be arranged within the wing span.
According to a different embodiment of the invention, the control surface can be arranged outside of the wing span. This achieves an effective enlargement of the wing span.
According to an embodiment of the invention, the control surface can be arranged behind the leading edge of the surface.
According to a different preferred embodiment, the control surface can be arranged in front of the leading edge of the surface. This achieves an enlargement of the lever with which the control surface acts relative to the elastic axis.
According to a preferred embodiment of the invention, the control surface can be provided in addition to a wing tip surface (winglet) on the surface end or tip.
According to a different preferred embodiment of the invention, the control surface itself can be embodied as a wing tip surface (winglet).
In this regard it is advantageously provided that the rotation axis of the control surface forming the wing tip surface extends slopingly or obliquely relative to the direction of the elastic axis.
In the two just-mentioned embodiments, the surface is advantageously especially a lifting wing of a flying machine, whereby the wing tip surface (winglet) continues the lifting wing at its end, sloping obliquely or extending vertically upwardly.
In this regard, the surface is especially a lifting wing of a flying machine, whereby the wing tip surface (winglet) continues the lifting wing, sloping obliquely or extending vertically upwardly, and the control surface continues the lifting wing in its direction or continues the lifting wing sloping obliquely downwardly. In combination with the winglet, the control surface results in a second wing tip, whereby two edge or tip vortices are formed, which similarly contributes to the reduction of the induced resistance or drag.
According to preferred embodiments and applications of the invention, the surface is the lifting surface of an aircraft.
Alternatively, the surface can be the lifting surface of a rotary wing aircraft.
According to an advantageous embodiment of the invention, a control arrangement is provided, which produces an adjusting or actuating signal for the control surface from data relating to the aircraft loading and the flight condition, while using stored desired or nominal value data or comparison data.
According to a different advantageous embodiment of the invention, a regulating arrangement is provided, which produces an adjusting or actuating signal for the control surface by comparison of measured data, for example data measured in an optical manner, representing the actual elastic deformation of the fluid dynamically effective surface, with desired or nominal data representing a nominal or desired deformation of the fluid dynamically effective surface prescribed for the aircraft loading and the flight condition.
In the following, example embodiments of the invention will be explained in connection with the drawings. It is shown by:
Six different example embodiments of fluid dynamically effective surfaces, namely of lifting surfaces of an aircraft, are illustrated in the
An adjustable control surface 3, which is respectively differentiated with 3 a, 3 b, 3 c, 3 d, 3 e, 3 f in the various example embodiments, is respectively provided on the surface 1.
For all of the example embodiments illustrated in the
The control surface 3 is arranged offset by a prescribed spacing distance relative to the elastic axis EA, as it is the case with the control surfaces 3 a, 3 b, 3 c, 3 d, 3 e of the
In the example embodiments of the
In the example embodiments of the
In the example embodiments of
The control surface 3 can be arranged behind the leading edge of the surface 1, with respect to the direction of incident flow, as is the case with the control surfaces 3 a, 3 b of the
On the other hand, the control surface 3 can also be arranged in front of the leading edge of the surface 1, with respect to the direction of incident flow, as with the control surfaces 3 c, 3 d of the
The control surface 3 can be provided at the end or tip of the surface 1 additionally to a wing end or tip surface 2 (winglet), as is the case with the control surfaces 3 a, 3 b, 3 c, 3 e of the
As can be seen, the wing tip surface (winglet) 2 continues the lifting wing or rather the surface 1 at its end obliquely or vertically upwardly in the example embodiments illustrated in the
In the example embodiment of the
The diagram illustrated in
In a schematic illustration,
The principle for a fluid dynamically effective surface of a device moving in a fluid and its elastic deformation for minimizing the induced fluid dynamic drag, described above in connection with a lifting surface of an aircraft, is similarly transferable or applicable to other types of flying machines, such as to rotary wing aircraft, but also basically applies for other types of fluid dynamically effective surfaces of a device moving in a fluid.
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|International Classification||B64C5/08, B64C3/38, B64C27/46, B64C23/06, B64C27/615, B64C9/10, B64C13/00, B64C19/00|
|Cooperative Classification||Y02T50/34, Y02T50/32, Y02T50/145, B64C27/615, B64C9/10, B64C5/08, B64C3/38, B64C27/463, B64C23/076|
|European Classification||B64C9/10, B64C27/615, B64C5/08, B64C23/06A, B64C27/46B, B64C3/38|
|Jun 30, 2009||AS||Assignment|
Owner name: AIRBUS DEUTSCHLAND GMBH, GERMANY
Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:SCHWEIGER, JOHANNES;REEL/FRAME:022895/0853
Effective date: 20050606
|Sep 28, 2010||CC||Certificate of correction|
|May 31, 2011||AS||Assignment|
Owner name: AIRBUS OPERATIONS GMBH, GERMANY
Free format text: CHANGE OF NAME;ASSIGNOR:AIRBUS DEUTSCHLAND GMBH;REEL/FRAME:026360/0849
Effective date: 20090602
|Mar 14, 2013||FPAY||Fee payment|
Year of fee payment: 4
|Mar 28, 2017||FPAY||Fee payment|
Year of fee payment: 8